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Information × Registration Number 0221U107070, 0121U111995 , R & D reports Title Development of a new method for the thrust vector control of a rocket engine with the detonation shock wave effect on the gas flow in the nozzle popup.stage_title Head Ternova Kateryna V., Кандидат технічних наук Registration Date 26-12-2021 Organization Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine popup.description2  The object of study - gas-dynamic controls of the thrust vector of the rocket stage on the active part of the flight. The purpose of research at this stage is to develop circuit solutions for injecting gas detonation products into the supercritical part of the nozzle for implementing a new method of the thrust vector control of a rocket engine by disturbing the gas flow in the nozzle with a detonation wave. Preparation of experimental base for research. Research methods - simulation and experimental analysis methods of the control force creation with the gas flow perturbation in the nozzle by the detonation wave. The following results are obtained at this stage of work: - the problem state of the speed thrust vector control of the upper stage propulsion systems of launch vehicles is considered; - the scheme of detonation product injection into the supersonic part of the nozzle is developed; - the test research bench of gas-dynamic processes of gas stream perturbation in a nozzle with a detonation wave is equipped with the necessary elements and the program of experimental researches is developed. The results of the research will make it possible to develop high-speed gas-dynamic rocket stage control bodies based on the use of a detonation wave to disturb the gas flow in the critical part of the nozzle. Such characteristics of the rocket engine thrust vector control will allow, in particular, to develop an active system of avoiding collisions with space debris elements for advanced space stages of launch vehicles and increase the reliability of their flight in the external shock conditions. The obtained research results are intended to be used for improving the control systems for the upper stages of missiles. Product Description popup.authors Yevseienko Maksym V Vasyliv Stepan S popup.nrat_date 2022-03-09 Close